7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - INSPECT AREA AROUND OVERWING REFUELLING APERTURE A

MODIFICATION No. : None

This page transmits Revision No. 04 of Service Bulletin No. A310-

ADDITIONAL WORK

No additional work is required by this revision for aircraft 

any previous issue.

REASON

This revision is issued to include all A310 aircraft in the ef

effectivity has been extended due to the extended service goa

which now require post modification 05891, 05980 and 05981 ai

inspected.

Layout changes due to computerization of this revision are no

CHANGES

SUMMARY :

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Reason for the extension of the effectivity included.

— EFFECTIVITY

. Effectivity expanded to include all A310 aircraft.

— MANPOWER

. Manpower defined by Configs.

— Figure

. Summary Figure added.

PLANNING INFORMATION :
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

. 1.C.(1) Reason for extension of the effectivity included.

— Objective/Action

. 1.C.(2) Visual inspection included for A310-200 aircraft 

05891H5128 and Mod. No. 05981H5131 and all A310-300 airc

— Advantages

. 1.C.(3) Accomplishment of SB A310-57-2020 as an advantage 

— DESCRIPTION

. 1.D. Configs included.

— COMPLIANCE

— Accomplishment Timescale

. 1.E.(2) Standard sentence added. Defined by Configs.

— APPROVAL

. 1.F. Approval statement updated.

— MANPOWER

. 1.G. Defined by Config. and inspection method. Standard 

updated.

— REFERENCES

. 1.J. AMM and SRM references added.

MATERIAL INFORMATION :

— LIST OF MATERIALS - OPERATOR SUPPLIED

. 2.D. Operator supplied material added.

ACCOMPLISHMENT INSTRUCTIONS :

— GENERAL

. 3.A. Standard Warnings added.

2
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

— INSPECTION

. 3.B.(1) Config. 01 added.

. 3.B.(2) Worksteps for Config. 02 thru 03 added.

. 3.B.(3) Worksteps for Config. 04 added.

. 3.B.(4) Worksteps for Config. 05 added.

— REPAIR

. 3.C.(1) Config. 01 added.

. 3.C.(1)(a) FC and FH changed.

. 3.C.(2) Worksteps for Config. 02 and 03 added. Repair ins

updated.

. 3.C.(3) Worksteps for Config. 04 added. Repair instructio

. 3.C.(4) Worksteps for Config. 05 and Config. 06 added.

— TESTS

. 3.D. Test paragraph added.

— CLOSE-UP

. 3.E. Close-up paragraph added.

— Figure 1

. Config. 01 added to title.

— Figure 2

. Config. 01 added to title.

— Figure 3

. New Fig. added for Configs 02 and 03.

— Figure 4

. New Fig. added for Config. 04.

3
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Put this Revision Transmittal Sheet in front of the Service B

HISTORY OF PREVIOUS REVISIONS

If information is required for Revisions issued previous to t

check your copies of Revision Transmittal Sheets or contact A

REVISION SEQUENCE

ORIGINAL : Aug 13/86

REVISION No. : 01 — Apr 08/93

REVISION No. : 02 — Mar 28/95

REVISION No. : 03 — May 02/96

REVISION No. : 04 — May 21/07

4
7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - INSPECT AREA AROUND OVERWING REFUELLING APERTURE A

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During structural testing of the wing, fatigue cracks were found 

from the attachment holes around the refuelling aperture in the w

between ribs 13 and 14.

On A310-200 aircraft modification 05891H5128 (Service Bulletin A3

introduced a redesigned refuelling cap which does not require thi

attachment. It has a larger diameter aperture which removes the e

from which cracks originate.

On some A310-200 and on all A310-300 aircraft, production modific

05980H5130 and 05981H5131 introduced a similar design of refuelli

introduced by modification 05891H5128.

For A310-200 aircraft that are before modification 05891H5128 (Se

A310-57-2020), this Service Bulletin requires mandatory High Freq

Current (HFEC) inspections to be carried out in order to detect c

attachment holes around the overwing refuelling aperture.

The effectivity of this Service Bulletin has been extended to inc

aircraft upto the extended service goal (ESG). An ESG study has s

aircraft after modifications 05891H5128, 05980H5130 and 05981H5131 

detailed visual inspections in the area of the refuelling apertur

top skin between ribs 13 and 14.

For A310-200 aircraft after modification 05891H5128 (Service Bull

A310-57-2020) and modification 05981H5131 and all A310-300 aircra

visual inspection is required of the external top skin in the imm

surrounding the refuelling aperture and also internally for crack

adjacent stringer 7 and stringer 8.

For A310-200 aircraft that are before modification 05891H5128 (Se

A310-57-2020), if cracks are found during the HFEC inspection fro

attachment holes which extend away from the direction of the aper
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

AIRBUS. Further advice from AIRBUS will be required before the ne

Timely detection of cracks may reduce the necessity of carrying ou

repairs.

When Service Bulletin A310-57-2020 (Mod. No. 05891H5128) has been 

HFEC inspections are replaced by DVI.

EFFECTIVITY

This Service Bulletin is applicable to these operators :

34W 58X 82Z 85Z 99Y A1L ABD AIC ARG BAF BBC BLM CFC CSA DAH DGA D

IRA IRM IYE JAB JAV KAC KYV MGL MPD MPJ MWA PIA QAF QSC R1T RJA RO

SGX SUD TAP THY TSC UAE UZB WHT

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

EVALUATION TABLE

COMPLIANCE MANDATORY CANCELS INSPECTION S

AD Yes A/C OPERATION AFFECT

RELIABILITY AFFECTED No PAX COMFORT AFFECTED 

COST SAVING No ETOPS AFFECTED 

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED 

KIT PRICE (USD) No kit DEFUEL/VENTING 

2
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

MANPOWER

Config. 01

Config. 02 thru Config. 06

MATERIAL INFORMATION

AIRCRAFT DATA

None

APPENDICES

None

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

3
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

4
7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - INSPECT AREA AROUND OVERWING REFUELLING APERTURE A

MODIFICATION No. : None

This document contains AIRBUS PROPRIETARY INFORMATION and shall a

remain the property of AIRBUS; no intellectual property right or 

granted by AIRBUS in connection with any information contained in 

delivered on the express condition that said document and the inf

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

conditions herein), without AIRBUS' prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

310-203 310-204 310-222 310-304 310-308 310-322 310-

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

0162 0172 0191 0201 0217 0224 0230 0233 0237 024

0251 0254 0257 0260 0264 0267 0273 0278 0281 02

0293 0297 0300 0303 0309 0313 0316 0318 0320 03

0335 0338 0339 0342 0343 0345 0346 0349 0353 03

0360 0362 0364 0367 0369 0370 0372 0375 0378 03

0390 0392 0394 0397 0399 0400 0406 0407 0410 04

0419 0421 0422 0425 0427-0431 0434 0436 0437 04

0444-0449 0451-0458 0467 0468 0472 0473 0475 04

0480-0492 0494-0503 0519 0520 0522-0524 0526 05

0535 0537-0539 0541 0542 0544 0545 0547-0552 05

0567 0568 0571 0573 0574 0576 0585-0595 0597-060

0624 0634 0636 0638 0640 0642 0644 0646-0654 06

0661 0663 0665 0667 0669 0671 0672 0674 0676 06
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

from transfer of an aircraft from one operator t

not be reflected in this list unless the Service 

revised for another reason.

OPERATOR MSN

34W 0399

58X 0431

82Z 0550 0551

85Z 0524

99Y 0489

A1L 0648

ABD 0624

AIC 0392 0406 0407 0413 0428 0429 0501 0

0598 0654 0665 0669 0680 0684 0693 0

ARG 0640 0686

BAF 0367 0372

BBC 0594 0650 0698 0700

BLM 0488

CFC 0425 0441 0444 0446 0482

CSA 0564 0567 0672 0674

DAH 0291 0293

DGA 0418 0421 0422

DRD 0527

F2I 0309 0320

FDX 0162 0191 0201 0217 0224 0230 0233 0

0248 0251 0254 0257 0260 0264 0267 0

0283 0288 0297 0303 0313 0316 0318 0

0335 0339 0342 0343 0345 0346 0349 0

0359 0360 0362 0364 0369 0378 0394 0

0449 0452 0454 0456 0457 0458 0467 0

0539 0542 0549 0552 0589 0593 0634 0

GAF 0434 0484 0498 0499 0503 0522 0523

IRA 0338 0370 0375 0379 0389 0390 0436 0

IRM 0537 0586

IYE 0535 0568 0702 0704

JAB 0419

2
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(c) Effectivity by MSN and Kit/Configuration

The kits and configurations applicable to these 

at the end of this list:

0162 0172 0191 0201 0217 0224 0230 0233 0237 024

0251 0254 0257 0260 0264 0267 0273 0278 0281 02

0293 0297 0300 0309 0316 0318 0320 0326 0331 03

0338-0339 0342-0343 0345-0346 0349 0353 0355-03

0362 0364 0367 0369 0372 0375 0379 0386 0394

NOTE : Config. 01 is applicable to aircraft that 

Mod. No. 05891H5128 (SB A310-57-2020) emb

MPD 0451 0455 0642

MPJ 0410

MWA 0652

PIA 0585 0587 0590 0653 0656 0660 0676 0

0689 0691

QAF 0473

QSC 0620

R1T 0591

RJA 0416 0445 0490 0491 0531

ROT 0636 0644

RZO 0571 0651 0661

S8G 0300

SBI 0427 0430 0453 0468 0475 0486 0487 0

SGX 0519 0562

SUD 0437

TAP 0483 0494 0495 0541 0565 0573

THY 0386 0476 0478 0480 0496 0497 0502

TSC 0447 0472 0485 0545 0547 0588 0595 0

0658

UAE 0592 0622 0646 0667

UZB 0574 0576 0706

WHT 0448

KIT No. QTY PER A/C CONFIGURATION

01

3
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Config. 02 is applicable to aircraft that 

Mod. No.5891H5128 (SB A310-57-2020) and S

(Mod. No. 10685D20756) embodied.

The kits and configurations applicable to these 

at the end of this list:

0370 0389-0390 0397 0400

NOTE : Config. 03 is applicable to aircraft that 

05891H5128 (SB A310-57-2020) embodied and 

SB A310-00-2024 (Mod. No. 10685D20756) em

The kits and configurations applicable to these 

at the end of this list:

0378 0392 0399 0406-0407 0410 0413

NOTE : Config. 04 is applicable to aircraft that 

05980H5130 embodied and and do not have M

05981H5131 embodied.

The kits and configurations applicable to these 

at the end of this list:

0416 0418 0421-0422 0425 0428-0429 0431 0434 04

0441 0444-0449 0451-0453 0455-0458 0467 0472-04

0478 0480-0485 0488-0492 0494-0503 0519-0520 05

0526-0527 0531 0534-0535 0537-0539 0541-0542 054

0547-0552 0562 0564-0565 0567-0568 0571 0573-05

0585-0595 0597-0600 0620 0622 0624 0634 0636 06

0644 0646-0654 0656 0658 0660-0661 0663 0665 06

0671-0672 0674 0676 0678 0680 0682 0684 0686-06

0693 0695 0697-0698 0700 0702 0704 0706

02

KIT No. QTY PER A/C CONFIGURATION

03

KIT No. QTY PER A/C CONFIGURATION

04

4
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

The kits and configurations applicable to these 

at the end of this list:

0419 0427 0430 0454 0468 0486-0487

NOTE : Config. 06 is applicable to A310-200 airc

Mod. No. 05981H5131 embodied.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During structural testing of the wing, fatigue crack

that started from the attachment holes around the re

aperture in the wing top skin between ribs 13 and 14

On A310-200 aircraft modification 05891H5128 (Servic

A310-57-2020) introduces a redesigned refuelling cap 

require this type of attachment. It has a larger diam

which removes the existing holes from which cracks o

On some A310-200 and on all A310-300 aircraft product

modifications 05980H5130 and 05981H5131 introduced a 

of refuelling cap as that introduced by modification 

The effectivity of this Service Bulletin has been ext

include all A310 aircraft upto the extended service g

ESG study has shown that aircraft after modification

05980H5130 and 05981H5131 will now need detailed visu

in the area of the refuelling aperture in the wing to

ribs 13 and 14.

KIT No. QTY PER A/C CONFIGURATION

06

5
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

For A310-200 aircraft after modification 05891H5128 

Bulletin A310-57-2020) and modification 05981H5131 an

aircraft, a detailed visual inspection is required o

top skin in the immediate area surrounding the refue

and also internally for cracks in the adjacent string

stringer 8.

For A310-200 aircraft that are before modification 0

(Service Bulletin A310-57-2020), if cracks are found 

HFEC inspection from the attachment holes which exte

the direction of the aperture, the embodiment of the 

in its standard form will not be possible. Remedial 

then consist of either a variation of Mod 05891H5128 

Bulletin A310-57-2020), for short cracks, or a repai

reinforcing plate for longer cracks.

On A310-200 aircraft after modification 05891H5128 (

Bulletin A310-57-2020) and modification 05981H5131 

A310-300 aircraft, if cracks are found during the det

inspections they must be reported to AIRBUS. Further 

AIRBUS will be required before the next flight.

(3) Advantages

Timely detection of cracks may reduce the necessity o

non standard repairs.

When Service Bulletin A310-57-2020 (Mod. No. 05891H5

accomplished, HFEC inspections are replaced by DVI.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) Drain and vent the fuel tanks

(b) Get access to the tank bays (LH and RH) between 

14.

(c) Remove shield and adapter ring

6
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(h) Refuel tanks

(i) Carry out leak test.

(j) Close up and complete the documentation.

(2) Config. 02 thru Config. 06

(a) Drain and vent the fuel tanks

(b) Get access to the tank bays (LH and RH) between 

14.

(c) Do a detailed visual inspection (DVI) of the LH 

top skin between rib 13 and rib 14.

(d) Do a DVI of the internal area for cracks on str

stringer 8.

(e) If necessary, report any cracks to AIRBUS and aw

instructions.

(f) Close up tanks

(g) Refuel tanks

(h) Carry out leak test.

(i) Close up and complete the documentation.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is expected t

mandatory by the issue of an Airworthiness Directive 

by the European Aviation Safety Agency (EASA). It is 

that the AD will confirm the thresholds and interval

but reference should be made to the AD for confirmat

mandated accomplishment timescale.

For Config. 01 Aircraft

7
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

For Config. 02 Aircraft

A detailed visual inspection (DVI) on the top skin a

on the stringers is necessary within 30,900FC or 61,9

comes first from embodiment of SB A310-57-2020 (Mod. 

05891H5128).

For aircraft that have exceeded this threshold the i

necessary within 1500 FC or 18 months, whichever com

receipt of this Service Bulletin at Revision 04.

Repeat DVIs are necessary at every 11,300FC or 22,600

comes first.

For Config. 03

A DVI on the top skin and internally on the stringer

within 30,900FC or 61,900FH whichever comes first fro

of Mod. No. 05891H5128 (SB A310-57-2020).

For aircraft that have exceeded this threshold the i

necessary within 1500 FC or 18 months, whichever com

receipt of this Service Bulletin at Revision 04.

Repeat DVIs are necessary at every 12,000FC or 24,000

comes first.

For Config. 04 and Config. 05 Aircraft

Short Range

A DVI on the top skin and internally on the stringer

within 25,900FC or 72,500FH whichever comes first fro

delivery.

For aircraft that have exceeded this threshold the i

necessary within 1500 FC or 18 months, whichever com

receipt of this Service Bulletin at Revision 04.

Repeat DVIs are necessary at every 12,000FC or 33,600

comes first.

For Config. 04 and Config. 05 Aircraft

Long Range

8
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Repeat DVIs are necessary at every 9,400FC or 47,200

comes first.

For Config. 06

A DVI on the top skin and internally on the stringer

within 30,900FC or 61,900FH, whichever occurs first 

delivery.

For aircraft that have exceeded this threshold the i

necessary within 1500FC or 18 months, whichever occu

receipt of this Service Bulletin at Revision 04.

Repeat DVI are necessary at every 12,000FC or 24,000

occurs first.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are 

direct labor cost to do the work. These estimates assume 

will be done by experienced personnel, and may need to be 

upwards to suit operator's circumstances. The estimates do 

the time to prepare, plan or inspect the work. Manufactur

procurement of parts and tools, drying times for paints, 

and general administration work are also not included.

Config. 01

HFEC Inspection

Get access 

Inspection 

Close up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

9
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

Service Bulletin (SB): A310-57-2020

Service Bulletin (SB): A310-00-2024

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

None

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Aircraft Maintenance Manual (AMM) : 24-00-00 28-10-00 

28-11-22 28-12-00 

Non destructive Testing Manual (NTM) : 51-10-01, Part 6

51-60-00, Part 6

51-90-00, Part 9

Structural Repair Manual (SRM) : 51-40-21 51-40-44 

51-76-10 51-76-20

10
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

AIRBUS will not provide industry support for accomplishme

Service Bulletin.

C. LIST OF COMPONENTS

None

D. LIST OF MATERIALS — OPERATOR SUPPLIED

(1) Consumable Materials

(2) Components

None

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

None

F. TOOLING — PRICE AND AVAILABILITY

None

G. SPECIAL TOOLS

None

DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C 

Fuel Tank Sealant

Polysulfide

09-001 As required

Fuel Tank Sealant

Polysulfide

09-002 As required

Corrosion Inhibiting Fillet

Consistency

09-016 As required

11
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This Page Intentionally Left Blank

12
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSON

WARNING : MAKE SURE THAT THE GROUND SAFETY LOCKS ARE CORRE

ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING G

WARNING : OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A 

THIS WILL PREVENT INJURY OR DAMAGE.

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND TH

INCLUDED IN THE REFERENCED PROCEDURES.

(1) Preparation

(a) Config. 01 thru Config. 06

1 Make sure that the aircraft is electrically g

to AMM 24-00-00 Page block 301).

2 Put access platforms in position below the ac

540HB and 640HB on the LH and RH wings.

3 Defuel and ventilate the inner fuel tanks (Re

28-25-00 Page block 301 and AMM 28-10-00 Page 

4 Open the access panels 540HB and 640HB (Refe

28-11-22 Page block 401).

(2) Standard Practices

(a) For fastener removal and installation refer to 

(b) For fastener hole and drill data refer to SRM 5

(c) For fastener torque tightening refer to SRM 51-4

(d) For the repair of sealing refer to SRM 51-76-10

13
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(a) Remove and retain the six bolts which attach the 

remove the shield.

(b) Remove and retain the remaining six bolts and t

ring.

(c) Clean the bolt holes.

(d) Do a Rotating Probe HFEC inspection of the twelv

for cracks. (Refer to NTM 51-10-01 Part 6.)

(e) If cracks are found refer to the Para 3.C.(1) R

repair instructions.

(f) If no cracks are found and Mod 05891H5128 (Serv

A310-57-2020) is not to be embodied :

1 Clean all remaining traces of sealant from t

skin rebate and the inside face of the reinfo

2 Clean sealant from the mating faces of the s

adapter ring.

3 Repair any damaged protective treatments.

4 Assemble the adapter ring into the skin rebat

Tank Sealant Polysulfide (Mat No. 09-001) . 

attachment bolts using Fuel Tank Sealant Poly

No. 09-001) .

5 Fill the cavity between the adapter ring and 

with Fuel Tank Sealant Polysulfide (Mat No. 0

an extrusion gun and compact with a plastic 

6 While the sealant is still soft, assemble the 

applying Fuel Tank Sealant Polysulfide (Mat N

the mating face of the flange. Attach with t

six bolts using Fuel Tank Sealant Polysulfide 

09-001) .

7 Fill the skin rebate around the edge of the a

with Corrosion Inhibiting Fillet Consistency 

09-016) .

8 Make certain that the work areas are clean a

tools and miscellaneous items of equipment.

14
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(a) External DVI

1 Do a visual inspection of the area shown. Be 

to look for cracks between fasteners.

(b) Internal DVI

1 From inside the wing tank, use a good safe li

do a visual inspection of the stringer 7 and 

cracks in the area of the overwing refuel ape

careful to look for cracks between fasteners

(c) If cracks are found, refer to REPAIR, paragraph 

(3) Config. 04

Refer to Figure 4 , Sheet 1

(a) External DVI

1 Do a visual inspection of the area shown. Be 

to look for cracks between fasteners.

(b) Internal DVI

1 From inside the wing tank, use a good safe li

do a visual inspection of the stringer 7 and 

cracks in the area of the overwing refuel ape

careful to look for cracks between fasteners

(c) If cracks are found, refer to REPAIR, paragraph 

(4) Config. 05 thru Config. 06

Refer to Figure 5 , Sheet 1

(a) External DVI

1 Do a visual inspection of the area shown. Be 

to look for cracks between fasteners.

(b) Internal DVI

1 From inside the wing tank, use a good safe li

do a visual inspection of the stringer 7 and 

cracks in the area of the overwing refuel ape

careful to look for cracks between fasteners

15
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

extending from the bolt holes towards the cap a

Service Bulletin A310-57-2020 (Mod. No. 05891H5

accomplished as soon as possible, within a maxim

190FC/380FH whichever comes first. If Service B

A310-57-2020 (Mod. No. 05891H5128) is not accom

immediately, a further NDT check must be done be

accomplishment. This will ensure that the crack 

subsequently initiated from the other side of t

extending away from the aperture. If this has o

to paragraph 3.C.(1)(b) that follows.

(b) If a crack is detected in a bolt hole extending 

direction of the aperture, it must be repaired b

flight. If it is assessed to be 1mm (0.04in) or 

into the material beyond the bolt hole it can be 

follows :

1 Refer to Service Bulletin A310-57-2020 and em

05891H5128, up to and including reworking of 

aperture and removal of the reinforcing plate

2 Carry out initial blending and recheck for c

using an Eddy Current pencil probe (Refer to 

Part 6) or fluorescent dye penetrant (Refer t

Part 9). Continue blending until the crack i

removed or a maximum depth of 1.5mm (0.06in) 

3 If the crack is completely removed, within t

depth limit of 1.5mm (0.06in), extend the ble

removing a further 0.5mm (0.02in) of materia

maximum depth of 'D.'.

4 Complete the blending by profiling into the a

surface of adjacent blending as necessary. T

surface is to be smooth and have a polished 

5 Complete the embodiment of Mod 05891H5128 (Se

A310-57-2020) and in addition fill in the ble

Fuel Tank Sealant Polysulfide (Mat No. 09-002

fitting the new adapter.

6 If the crack is not completely removed when t

of 1.5mm (0.06in) is reached, refer to paragr

that follows.

(c) Further repair instructions will be required fro

if :

16
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

reporting form to AIRBUS.

(2) Config. 02 thru Config. 03

Refer to Figure 3 , Sheet 1

(a) External Detailed Visual Inspection

1 If any cracks are found in the inspection are

details of cracking to AIRBUS for a suitable 

the crack dimensions, direction and hole pos

(b) Internal Detailed Visual Inspection

1 If the stringer 7 or stringer 8 is found to 

report details of cracking to AIRBUS for a su

Give the crack dimensions, direction and hole 

(3) Config. 04

Refer to Figure 4 , Sheet 1

(a) External Detailed Visual Inspection

1 If any cracks are found in the inspection are

details of cracking to AIRBUS for a suitable 

the crack dimensions, direction and hole pos

(b) Internal Detailed Visual Inspection

1 If the stringer 7 or stringer 8 is found to 

report details of cracking to AIRBUS for a su

Give the crack dimensions, direction and hole 

(4) Config. 05 thru Config. 06

Refer to Figure 5 , Sheet 1

(a) External Detailed Visual Inspection

1 If any cracks are found in the inspection are

details of cracking to AIRBUS for a suitable 

the crack dimensions, direction and hole pos

(b) Internal Detailed Visual Inspection

1 If the stringer 7 or stringer 8 is found to 

report details of cracking to AIRBUS for a su

Give the crack dimensions, direction and hole 

17
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(a) Make sure that the work areas are clean and clea

other items of equipment.

(b) Close the access panels 540HB and 640HB, AMM 28

block 401.

(c) Remove the access platforms.

(d) Remove all the warning notices that were positio

Accomplishment Instructions.

(e) Refuel the fuel tanks (Refer to AMM 28-25-00 Pag

(f) Do a fuel leak test (Refer to AMM 28-11-00 Page 

(g) Put the aircraft back to normal operational cond

F. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

18
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 1

Config. 01:View of Top Skin Rib 13-14

19
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 2 Sheet 1

Config. 01:View of Typical Crack Locations

20
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 3 Sheet 1 (Goto A3 section)

Config. 02 thru 03:Inspection Area

21
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 4 Sheet 1 (Goto A3 section)

Config. 04:Inspection Area

23
DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 5 Sheet 1 (Goto A3 section)

Config. 05 and 06:Inspection Area

25
7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

A - SB WILL BE embodied............. YES/NO (if NO p

If YES, aircraft concerned (as per SB effectivity by default) and 

(month/year) of embodiment:...................

.................................

.................................

B - SB HAS BEEN embodied on aircraft:..............

.................................

.................................

Operator comments:.......................

................................

................................

From Airline:..........................

Name/Title:...........................

Signature:.............. Date:......

If operational documentation is affected (see Paragraph 1.K of th

information is needed prior to next normal revision or prior to S

please indicate required service:

Either: Modification Operational Impact (MOI), if available. . YE

Or : Intermediate revision. ................ YE

Important Information: This SB will only be incorporated in your m

operational documentation if this sheet is returned to Airbus and 

duly authorised representative. With the next feasible revision, 

result in

- updating of maintenance documentation to show pre and post S

- updating of maintenance and operational documentation to show 

after embodiment.

If this SB requires previous or simultaneous accomplishment of ot

Airbus shall automatically include them in the manual revisions. 

00-037 for detailed information.

Please return this completed sheet to:

 AIRBUS

 CUSTOMER SERVICES DIRECTORATE

 1 Rond Point Maurice Bellonte

 31707 BLAGNAC CEDEX FRANCE

 Attn: SDC32 Technical Data and Documentation Services

 FAX: (+33) 5 61 93 28 06

 e-mail: sb.reporting@airbus.com

 or via your Resident Customer Support Office.

 Alternatively, SB lists via letters or fax are also accepted.
7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310

REVISION No. : 04 — May 21/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(Please rate on a scale of 1 to 4, with 4 being the 

- Quality rating of this SB 

- Quality rating of the Accomplishment Instructions 

- Quality rating of the Illustrations 

- Is this SB easy to understand ? 

If you have had difficulties in the accomplishment of this SB plea

the area(s) and give a short description of the issue.

Planning Material Instruct

X Effectivity X Kit content X Preparat

X Reason X List of Materials X Mod/Insp

X Manpower Operator Supplied X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustra

Comments :

Operator : Date:

Name/Title :

Please return this form to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.
@ A310

SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006REVISION No. : 04 — May 21/07 Page : 21/22

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 3 Sheet 1

Config. 02 thru 03:Inspection Area
@ A310

SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006REVISION No. : 04 — May 21/07 Page : 23/24

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 4 Sheet 1

Config. 04:Inspection Area
@ A310

SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006REVISION No. : 04 — May 21/07 Page : 25/26

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 5 Sheet 1

Config. 05 and 06:Inspection Area